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An experimental and computational study of the flow in a transonic compressor rotor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1976], 1976)
A comprehensive investigation of the flow field produced by an isolated transonic compressor rotor has been completed. This rotor has an overall diameter of two feet, an inlet hub/tip ratio of 0.5, a tip Mach number of 1.2 ...
Asymptotic analysis of numerical wave propagation in finite difference equations
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1983], 1983)
An asymptotic technique is developed for analysing the propagation and dissipation of wave-like solutions to finite difference equations. It is shown that for each fixed complex frequency there are usually several wave ...
Exit flow from a transonic compressor rotor
(Cambridge : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1975], 1975)
Summary: The three dimensional unsteady flow field behind a transonic compressor rotor with a design pressure ratio of 1.6 at a tip Mach number of 1.2 has been resolved on the blade-passing time scale, using the M.I.T. ...
FORTRAN program for calculating three-dimensional, inviscid, rotational flows with shock waves in axial compressor blade rows : I--user's manual
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1981], 1981)
Summary: A FORTRAN-IV computer program has been developed for the calculation of the inviscid transonic/supersonic flow field in a fully three-dimensional blade passage of an axial compressor rotor or stator. Rotors may ...